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EP0314568B1 - Moteur d'aviation à très grand taux de dilution et ses intégrations sous l'aile d'un avion - Google Patents

Moteur d'aviation à très grand taux de dilution et ses intégrations sous l'aile d'un avion Download PDF

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Publication number
EP0314568B1
EP0314568B1 EP88402693A EP88402693A EP0314568B1 EP 0314568 B1 EP0314568 B1 EP 0314568B1 EP 88402693 A EP88402693 A EP 88402693A EP 88402693 A EP88402693 A EP 88402693A EP 0314568 B1 EP0314568 B1 EP 0314568B1
Authority
EP
European Patent Office
Prior art keywords
engine
wing
nacelle
casing
outer casing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP88402693A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0314568A1 (fr
Inventor
Alain Marie Joseph Lardellier
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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Filing date
Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0314568A1 publication Critical patent/EP0314568A1/fr
Application granted granted Critical
Publication of EP0314568B1 publication Critical patent/EP0314568B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings or cowlings
    • B64D29/02—Power-plant nacelles, fairings or cowlings associated with wings

Definitions

  • the present invention relates to a nacelle for suspending under the wing of an aircraft a turbojet group double flow with very high dilution rate of the type known as rear contrafan according to the preamble of claim 1.
  • a nacelle is known from GB-A- 2,188,987.
  • turbojet groups have been produced with a very high dilution rate, one gas generator of which drives counter-rotating free turbines which are themselves integral with large, non-shrouded counter-rotating propellers.
  • Such motors allow flux dilution rates of between 30 to 40 which makes it possible to hope for savings of 20 to 25% on specific consumption.
  • the disadvantage of these engines lies in the large diameter of their propellers, which has hitherto required the arrangement of turbojet engines of this type laterally to the fuselage of the aircraft, and limits their use to the twin-engine formula.
  • Another object of the invention is to provide a nacelle structure which allows such engines to be hung under the wing of aircraft and no longer only on the sides of the fuselage of the aircraft.
  • Another object of the invention is to provide a nacelle which allows, by movable cowling, to facilitate the maintenance of engines of this type, that they are placed under the wing as proposed by one of the provisions of the invention, or conventionally mounted in a "pod", that is to say at a distance from the wing, as proposed by the variant of the invention.
  • Another object is to produce for these engines a nacelle comprising movable flaps making it possible to control the opening of the secondary nozzle according to the flight conditions and to integrate a flow reverser of simple construction.
  • a last aim is to use the movable flaps (in this case of small size) as openings facilitating the operation in reverse flow, in the case where the propellers are provided with a variable setting device allowing the reversal of flow, and adaptation to flight conditions.
  • the subject of the invention is therefore a nacelle for suspending under the wing of an airplane a turbojet group double flow with very high dilution rate of the so-called rear contrafan type comprising a gas generator driving two nested counter-rotating free turbines integral with propellers contra-rotating fairings located downstream of the gas generator, said nacelle comprising, in known manner, an inner casing of generally cylindrical shape surrounding the engine casing and forming the internal wall of the cold flow stream and capable of opening in a known manner for carrying out the work maintenance and an external cowling also of generally cylindrical shape whose internal edge forms the external wall of the cold flow stream and whose external edge forms the envelope of the nacelle.
  • the turbojet engine group is suspended from the wing of the airplane by a mast comprising two arms arranged in a vertical plane containing the longitudinal axis of the turbojet engine, arm contained in a streamlined streamlined fairing, and the upper ends of which are linked to a structural box of the wing and the lower ends are secured to a horizontal lifter of longitudinal axis disposed between the crankcase and the inner cowling, the turbojet engine group being attached to the lifter.
  • the upper ends of the arms of the mast are connected to the structural box of the wing by an aircraft suspension mast of conventional type and the external cowling is connected in its upper part to said aircraft suspension mast.
  • the upper ends of the arms of the mast are integral with the structural box of the wing and the thickness of the outer casing, between the inner and outer edges of said outer casing is, in its part upper, integrated with the thickness of the aircraft wing.
  • the outer edge of said cowling is connected to the underside of the wing by a profile of the Karman type which evolves from upstream to downstream and in an axial longitudinal plane situated vertical to the longitudinal axis of the group.
  • turbojet engine the generator defining the inner edge of the outer cowling is generally tangent to the underside of the wing seen in longitudinal section.
  • a particularly advantageous arrangement of the invention consists in that the cowling is in two shells of approximately 120 ° angle mounted on longitudinal hinges, which allows quite excellent accessibility of the propeller and engine part, when these shells are open for maintenance.
  • turbojet engine group is attached to the lifter, by the upstream end of the latter on the crankcase in line with the inlet guide vanes and by the downstream end of the latter.
  • transition structure located between the low pressure turbine and the free turbines.
  • FIG. 1 shows a turbojet engine group 1 comprising a double-body gas generator composed of two compressors 2 delivering compressed air to an annular combustion chamber 3 where it is mixed with fuel, this mixture being burned to be relaxed and provide some of the energy thus accumulated at two high and low pressure turbines 4 driving the compressors 2.
  • a turbojet engine group 1 comprising a double-body gas generator composed of two compressors 2 delivering compressed air to an annular combustion chamber 3 where it is mixed with fuel, this mixture being burned to be relaxed and provide some of the energy thus accumulated at two high and low pressure turbines 4 driving the compressors 2.
  • Downstream of this gas generator and after a fixed transition structure 5 are arranged two nested counter-rotating free turbines 6 and 6a which receive the energy from the expanded air downstream of the turbine 4 to drive two counter-rotating propellers 7 and 7a stirring cold air in a secondary annular stream 8 surrounding an inner cowling generally referenced 9 and of generally cylindrical shape, the cowling 9 being itself disposed around the crankcase 10.
  • the secondary stream 8 internally de
  • turbojet engine unit being thus briefly described, its first mode of attachment under the wing of an aircraft as well as the production of the rollovers will be explained with reference to all of FIGS. 1 to 8.
  • the wing 14 comprises a structural box 15 comprising in the longitudinal plane of the motors a longitudinal box beam 16 whose upstream part 16a is completely integrated inside the leading edge 14a of the wing and whose downstream part 16b crosses the lower surface 14b of the wing and extends under the lower surface to the right of the trailing edge 14c of the wing.
  • two arms 17a and 17b, contained in a spindle fairing 18, have their lower end secured to a horizontal lifting beam 19 disposed between the motor housing 10 and the inner cowling 9.
  • the turbojet engine is attached to this spreader 19 upstream by three rods 20 at the level of the guide vanes inlet 21 and downstream by three links 22 suspended from two transverse support arms respectively upstream 23 and downstream 24 integral with the lifter.
  • the lifter also includes upstream ears 25 on which the movable cowls 9a, 9b of the inner cowling 9 are articulated, the latter also being articulated at the downstream end of the lifter on downstream supports 26 integral with the lifter (FIG. 2).
  • the external cowling 12 of the nacelle 13, for its part, is, in cross section, separated into three sectors 12a, 12b, 12c of 120 ° each, the upper sector 12a being symmetrical with respect to the longitudinal vertical plane 1.
  • the ferrule forming the inner wall 11 of the outer cowling is also separated in the same way into three sectors.
  • retention structures 39 (fig 1) allowing energy to be absorbed in the event of one of the propeller blades breaking.
  • the upper sector 11a is hooked by axes 28 to double transverse brackets 27b, 27c, 27d, 27e integral with the beam 16c respectively located in the cutting planes B, C, D, E., so that the bracket 27c and the stem 27e are arranged respectively upstream and downstream of the counter-rotating propellers.
  • the two lower sectors 12b and 12c are movable around articulations 29 b, c, d, e, of the structural box 15 of the wing, a partial view according to F1 is shown in FIG. 5a, said box connecting laterally to the 'intrados 14b, of the wing by a Karman profile 30 evolving from upstream to downstream.
  • the two shells 12b and 12c can open upwards in order to leave access to the motor or close and be locked in 12d at the bottom by a known locking means.
  • the sectors 9 and 9b of the inner cowling 9 can be articulated at 31 (FIGS. 2 and 4) in order to allow access to the engine.
  • Movable flaps 32 are arranged downstream of the counter-rotating propellers 7, 7a on at least the two lower sectors 12b, 12c of the outer cowling.
  • the upper sector 12a of the cowling 12 also includes a movable flap 32.
  • Each of these flaps is made mobile by two screw jacks 33, (shown in Figure 7 and arranged in the thickness of the cover in 34 Figure 6) from a first position where the flaps are located in the extension of the outer cover (in solid lines in Figures 1 and 7) to a second position intermediate folded towards the axis of the turbojet (in dashed lines in FIG. 7) so as to allow a variation in cross section of the secondary nozzle, this in order to optimize the dilution rate as a function of the operating parameters of the engine.
  • the flaps 32 can be moved in translation downstream and in rotation from their first or second position since in a third position (in phantom in Figure 1) where they are completely folded down towards the inner cowling 9 and discover grids of the outside cowling (not shown). The flaps 32 then behave in this 3rd position as thrust reverser doors for the secondary flow of the turbojet engine.
  • a similar arrangement (with smaller flaps and scooping outwards) could be adopted if the propellers have variable timing.
  • the intermediate positions of the flaps are no longer useful because the variable setting allows the motor to be adjusted; the wide open position facilitates the reverse flow of air when the propellers are in thrust reversal position.
  • the whole of the nacelle is stiffened upstream by a radial structural arm 35, said arm passing through (and being integral with) the crankcase and the interior and exterior cowlings.
  • a radial structural arm 35 said arm passing through (and being integral with) the crankcase and the interior and exterior cowlings.
  • three structural arms 36 at 120 ° and two casing ferrules 10 and 37 are intended to stiffen the structure 12b and 12c, and to stabilize the inner barrel of the engine 43.
  • the structural arms 36 slide at their ends on axes 38 arranged parallel to the motor axis. This sliding is also used during the disassembly of the engine: in fact, to release the centering and labyrinths 40a, b, c, d the coupling 41 of the casing 37 is dismantled on the engine, and the rear end is moved backwards. central body 42, the covers 12b and 12c being open.
  • the engine can then be removed from the lifter as described above, the central rear body remaining on the aircraft. If we just open the covers 9a, 9b and 12b, 12c, we get perfect access to the propellers and the gas generator for routine maintenance operations.
  • This entire structure allows significant savings in fuel consumption by reducing the drag of the nacelle, facilitates engine maintenance by means of the opening side covers and facilitates the integration of an efficient thrust reverser on the rear contrafans.
  • the nacelle In this attachment mode, the nacelle is mounted in a "pod" in a conventional manner.
  • An aircraft support mast 116 is suspended from the structural beam 16 of the wing 14 by means of axes 117 and a hooking structure of common type and which will not be described further.
  • the upper part 12a of the nacelle is then hooked by the upper ends of the arms 17a and 17b and by the double transverse brackets 27b..27c to the lower part of the mast 116.
  • the fact that the engine is separated from the lower surface of the wing by the height of the mast 116 makes it possible to produce a flow reverser having either two, three or four tilting doors 32, according to the necessities of the aircraft manufacturer, which improves the efficiency of the reserve, without disturbing the flow of the flow along the lower surface of the wing.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP88402693A 1987-10-28 1988-10-26 Moteur d'aviation à très grand taux de dilution et ses intégrations sous l'aile d'un avion Expired - Lifetime EP0314568B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8714898A FR2622507B1 (ru) 1987-10-28 1987-10-28
FR8714898 1987-10-28

Publications (2)

Publication Number Publication Date
EP0314568A1 EP0314568A1 (fr) 1989-05-03
EP0314568B1 true EP0314568B1 (fr) 1991-04-24

Family

ID=9356240

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88402693A Expired - Lifetime EP0314568B1 (fr) 1987-10-28 1988-10-26 Moteur d'aviation à très grand taux de dilution et ses intégrations sous l'aile d'un avion

Country Status (5)

Country Link
US (1) US4940196A (ru)
EP (1) EP0314568B1 (ru)
JP (1) JPH0829759B2 (ru)
DE (1) DE3862566D1 (ru)
FR (1) FR2622507B1 (ru)

Families Citing this family (23)

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FR2645911B1 (fr) * 1989-04-18 1991-06-07 Snecma Moteur a grand taux de dilution a soufflante amont et soufflante aval
FR2661213B1 (fr) * 1990-04-19 1992-07-03 Snecma Moteur d'aviation a tres grand taux de dilution et du type dit contrafan avant.
FR2676707B1 (fr) * 1991-05-23 1993-08-13 Snecma Nacelle pour suspendre sous l'aile d'un avion un groupe turboreacteur du type a double flux.
US5307623A (en) * 1991-05-28 1994-05-03 General Electric Company Apparatus and method for the diassembly of an ultra high bypass engine
US5174525A (en) * 1991-09-26 1992-12-29 General Electric Company Structure for eliminating lift load bending in engine core of turbofan
JP2606289Y2 (ja) * 1993-06-07 2000-10-10 富士重工業株式会社 航空機のナセル装置
US5467941A (en) * 1993-12-30 1995-11-21 The Boeing Company Pylon and engine installation for ultra-high by-pass turbo-fan engines
FR2764644B1 (fr) * 1997-06-12 1999-07-16 Hispano Suiza Sa Turboreacteur a double flux associe a un inverseur de poussee avec un carenage rapporte dans la veine fluide
US6725542B1 (en) * 1999-09-17 2004-04-27 Alan R Maguire Method of assembling a gas turbine engine and nacelle
GB0312490D0 (en) * 2003-06-02 2003-07-09 Rolls Royce Plc Aeroengine nacelle
FR2856379B1 (fr) * 2003-06-18 2006-11-24 Airbus France Moteur d'avion dont les capots de soufflante et d'inverseurs de poussee sont separes par un jeu reduit
US6824092B1 (en) 2003-10-30 2004-11-30 Supersonic Aerospace International, Llc Aircraft tail configuration for sonic boom reduction
GB0401189D0 (en) * 2004-01-21 2004-02-25 Rolls Royce Plc Turbine engine arrangements
FR2905991B1 (fr) * 2006-09-20 2012-01-13 Snecma Systeme propulsif integre comportant un moteur a turboreacteur a double flux.
US9126691B2 (en) * 2007-05-30 2015-09-08 United Technologies Corporation Access door for gas turbine engine components
FR2933957B1 (fr) * 2008-07-18 2010-07-30 Airbus France Dispositif pour ceinturer une nacelle d'aeronef
US8720815B2 (en) 2010-04-27 2014-05-13 Rolls-Royce Corporation Aircraft propulsion system
US9233757B2 (en) 2011-11-10 2016-01-12 Rohr, Inc. Nacelle
WO2015010315A1 (en) 2013-07-26 2015-01-29 Mra Systems, Inc. Aircraft engine pylon
DE102015206093A1 (de) * 2015-04-02 2016-10-06 Rolls-Royce Deutschland Ltd & Co Kg Triebwerksverkleidung einer Fluggasturbine
US10737797B2 (en) * 2017-07-21 2020-08-11 General Electric Company Vertical takeoff and landing aircraft
RU2745276C1 (ru) * 2020-06-03 2021-03-23 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Капот газогенератора турбореактивного двигателя
US12091181B2 (en) 2021-12-13 2024-09-17 Spirit Aerosystems, Inc. Aircraft engine attachment assembly

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GB1098638A (en) * 1966-02-04 1968-01-10 Standard Telephones Cables Ltd Amplifier with binary output
US4055041A (en) * 1974-11-08 1977-10-25 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Integrated gas turbine engine-nacelle
FR2291091A1 (fr) 1974-11-13 1976-06-11 Snecma Dispositif de montage sur avion d'un turboreacteur
US3979087A (en) * 1975-07-02 1976-09-07 United Technologies Corporation Engine mount
US4147029A (en) * 1976-01-02 1979-04-03 General Electric Company Long duct mixed flow gas turbine engine
US4449682A (en) * 1979-01-03 1984-05-22 The Boeing Company Aerodynamically contoured, low drag wing, engine and engine nacelle combination
JPS5945559A (ja) * 1982-09-08 1984-03-14 Toshiba Corp 制御装置
FR2560854B1 (fr) * 1984-03-07 1986-09-12 Snecma Capotages structuraux participant a la rigidite d'ensemble d'un turboreacteur
GB2188987B (en) * 1986-04-09 1990-02-14 Rolls Royce A turbofan gas turbine engine and mountings therefor
US4801058A (en) * 1987-02-05 1989-01-31 Rolls-Royce Plc Aircraft and powerplant combinations

Also Published As

Publication number Publication date
EP0314568A1 (fr) 1989-05-03
JPH01202598A (ja) 1989-08-15
US4940196A (en) 1990-07-10
JPH0829759B2 (ja) 1996-03-27
FR2622507A1 (ru) 1989-05-05
FR2622507B1 (ru) 1990-01-26
DE3862566D1 (de) 1991-05-29

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